EP 1115963 B1 20030730 - GAS TURBINE ENGINE
Title (en)
GAS TURBINE ENGINE
Title (de)
GASTURBINE
Title (fr)
TURBOMACHINE
Publication
Application
Priority
- US 9920886 W 19990924
- US 16111598 A 19980925
Abstract (en)
[origin: WO0020740A2] A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.
IPC 1-7
IPC 8 full level
F01D 5/08 (2006.01); F01D 5/18 (2006.01); F01D 9/02 (2006.01); F01D 9/04 (2006.01); F01D 9/06 (2006.01); F02C 3/067 (2006.01); F02C 3/10 (2006.01); F02C 3/36 (2006.01); F02C 7/18 (2006.01); F04D 27/02 (2006.01)
CPC (source: EP KR US)
F01D 5/081 (2013.01 - EP US); F01D 5/187 (2013.01 - EP US); F01D 9/023 (2013.01 - EP US); F01D 9/04 (2013.01 - EP US); F01D 9/065 (2013.01 - EP US); F02C 3/365 (2013.01 - EP US); F02C 7/18 (2013.01 - EP KR US); F04D 27/0215 (2013.01 - EP US)
Designated contracting state (EPC)
CH DE FR GB LI SE
DOCDB simple family (publication)
WO 0020740 A2 20000413; WO 0020740 A3 20000706; WO 0020740 B1 20000803; AU 2471600 A 20000426; CA 2345293 A1 20000413; CN 1324433 A 20011128; DE 69910052 D1 20030904; DE 69910052 T2 20040527; EP 1115963 A2 20010718; EP 1115963 B1 20030730; JP 2003520315 A 20030702; KR 20010085844 A 20010907; US 2002104317 A1 20020808; US 6305157 B1 20011023; US 6453674 B1 20020924
DOCDB simple family (application)
US 9920886 W 19990924; AU 2471600 A 19990924; CA 2345293 A 19990924; CN 99812683 A 19990924; DE 69910052 T 19990924; EP 99968017 A 19990924; JP 2000574820 A 19990924; KR 20017003791 A 20010324; US 16111598 A 19980925; US 93006201 A 20010814